Pneumatic shape structure of multistage axial flow compressor

Abstract

The present disclosure provides an aerodynamic shape structure of a multi-stage axial flow compressor, comprising: a plurality of rotors for converting mechanical energy into air kinetic energy, and converting the passing air kinetic energy into potential energy by changing the direction of airflow; a plurality of stators for By changing the direction of the air flow, the kinetic energy of the passing air is converted into potential energy, and the direction of the air flow is adjusted to be consistent with the axial direction of the compressor; the rotors of the plurality of rotors and the stators of the plurality of stators are interspersed in sequence. an adjustable inlet part, arranged on the intake side of the plurality of rotors and the plurality of stators, for reducing the aerodynamic load of the tip of the first-stage rotor and increasing the aerodynamic load of the blade root of the first-stage rotor; and an outlet rectifying part, which is arranged on the air outlet sides of the plurality of rotors and the plurality of stators, and is used to convert the passing air kinetic energy into potential energy by changing the direction of the air flow, and can adjust the air flow direction to be compatible with the compressor. axis direction is the same.

Description

technical field [0001] The present disclosure relates to the technical field of turbo machinery, and in particular, to an aerodynamic shape structure of a multi-stage axial flow compressor. Background technique [0002] The compressor is one of the important components of the gas turbine engine. Its function is to provide compressed high-pressure, high-temperature gas to the combustion chamber. Due to the inherent characteristics of inverse pressure gradient, height three-dimensional, and highly unsteady, it is very difficult to develop the aerodynamic shape of the compressor. Especially the aerodynamic shape of the multi-stage high-pressure compressor, inter-stage matching and performance optimization under all working conditions are very difficult. Although the design system is constantly improving, due to the continuous improvement of design indicators, the design of multi-stage axial compressors is still One of the bottleneck technologies of the engine. Compared with for...

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Problems solved by technology

In particular, the aerodynamic shape of multi-stage high-pressure compressors, inter-stage matching and performance optimization under all working conditions are very difficult. Although the design system is constantly improving, the design of multi-stage axial flow compressors is still limited due to the continuous improvement of design indicators. One of the bottleneck technologies of the engine, compared with foreign advanced engine companies, the multi-stage axial flow compressor development in my country relies more on personal experience and judgment due to the lack of practical engineering design specifications and the support of a large number of test data. The degree of certainty is greater, and there is no public release of the results of the aerodynamic shape of the axial flow compressor exceeding ten levels

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